Research on aerodynamic performance and noise reduction of non-uniform serrated trailing edges for an axial compressor

With the growing demands for aerodynamic performance and noise control in modern fighter aircraft, traditional flow-field control approaches based on blade geometry have increasingly demonstrated limitations. Drawing inspiration from the serrated bionic characteristics of feathers, an optimization method based on non-uniform serrated trailing edges (NUSTEs) was developed to enhance aerodynamic performance and reduce noise. First, considering the rotor–stator interaction, the three-dimensional flow field model of the axial compressor was established. Using the detached eddy simulation method, the influence of different serration heights on the aerodynamic performance, acoustic characteristics, and internal dynamics was analyzed, and the possible mechanism for noise reduction and vortex structure was investigated. Furthermore, the relationship between wake velocity and serration parameters was explored to develop the design methodology for NUSTEs, with the objective of optimizing flow characteristics at different blade heights. The results indicate that the serrated trailing edge (STEs) effectively promote earlier mixing of the airflow at the serration root, breaking up large-scale bubble-like vortices into smaller tubular vortices, and mitigating pressure pulsations in the wake region, thereby reducing aerodynamic noise. Compared to uniform STEs, NUSTEs enhance turbulent mixing near the blade root by adjusting serration parameters at different blade heights, while suppressing leakage vortices near the blade top. NUSTEs exhibit superior vortex suppression and noise attenuation in the wake region, particularly near the blade top, significantly improving the overall performance of the axial compressor. This study offers theoretical and technical support for the aeroelastic optimization of aero-engine blades, with significant implications for engineering applications.